XFOIL Version 6.96 Calculated polar for: BOEING 707 .99 SPAN AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4698 0.08126 0.07904 -0.0345 1.0000 0.0109 -8.000 -0.4990 0.06956 0.06735 -0.0380 1.0000 0.0105 -7.500 -0.5015 0.05900 0.05658 -0.0413 0.9961 0.0112 -7.250 -0.4863 0.05650 0.05404 -0.0433 0.9895 0.0117 -6.750 -0.4470 0.05042 0.04775 -0.0478 0.9734 0.0132 -6.500 -0.4236 0.04632 0.04345 -0.0503 0.9635 0.0139 -6.250 -0.3858 0.04405 0.04088 -0.0520 0.9526 0.0161 -5.750 -0.3393 0.03435 0.03061 -0.0567 0.9099 0.0148 -5.500 -0.3152 0.03091 0.02681 -0.0569 0.8831 0.0147 -5.250 -0.2946 0.02824 0.02378 -0.0559 0.8631 0.0147 -5.000 -0.2739 0.02596 0.02118 -0.0546 0.8494 0.0149 -4.750 -0.2524 0.02397 0.01890 -0.0535 0.8390 0.0151 -4.500 -0.2288 0.02258 0.01725 -0.0525 0.8303 0.0156 -4.000 -0.1833 0.01915 0.01328 -0.0505 0.8160 0.0156 -3.750 -0.1594 0.01751 0.01142 -0.0497 0.8100 0.0154 -3.500 -0.1344 0.01616 0.00985 -0.0490 0.8044 0.0154 -3.250 -0.1087 0.01509 0.00860 -0.0485 0.7994 0.0156 -3.000 -0.0828 0.01429 0.00766 -0.0480 0.7939 0.0159 -2.750 -0.0566 0.01386 0.00711 -0.0476 0.7887 0.0163 -2.500 -0.0311 0.01279 0.00594 -0.0472 0.7836 0.0167 -2.250 -0.0059 0.01197 0.00506 -0.0467 0.7784 0.0169 -2.000 0.0185 0.01124 0.00428 -0.0461 0.7739 0.0177 -1.750 0.0437 0.01080 0.00383 -0.0456 0.7688 0.0184 -1.500 0.0686 0.01037 0.00337 -0.0450 0.7634 0.0183 -1.250 0.0937 0.01003 0.00298 -0.0445 0.7583 0.0181 -1.000 0.1190 0.00972 0.00265 -0.0440 0.7519 0.0180 -0.750 0.1444 0.00948 0.00235 -0.0435 0.7453 0.0179 -0.500 0.1701 0.00925 0.00210 -0.0431 0.7374 0.0179 -0.250 0.1953 0.00906 0.00186 -0.0425 0.7231 0.0180 0.000 0.2198 0.00894 0.00162 -0.0417 0.6984 0.0183 0.250 0.2445 0.00887 0.00143 -0.0410 0.6735 0.0187 0.500 0.2685 0.00889 0.00128 -0.0402 0.6386 0.0195 0.750 0.2924 0.00897 0.00118 -0.0393 0.6005 0.0212 1.000 0.3162 0.00911 0.00113 -0.0385 0.5528 0.0242 1.250 0.3252 0.00811 0.00112 -0.0357 0.4496 0.5667 1.500 0.3377 0.00871 0.00142 -0.0330 0.2907 0.6673 1.750 0.3526 0.00880 0.00163 -0.0305 0.2145 0.7858 2.000 0.3779 0.00944 0.00207 -0.0302 0.0572 0.9288 2.250 0.4356 0.00978 0.00232 -0.0370 0.0352 0.9727 2.500 0.4685 0.00994 0.00245 -0.0382 0.0337 0.9799 2.750 0.5012 0.01011 0.00261 -0.0395 0.0330 0.9861 3.000 0.5338 0.01029 0.00278 -0.0407 0.0325 0.9918 3.250 0.5663 0.01047 0.00299 -0.0420 0.0323 0.9968 3.500 0.5987 0.01067 0.00321 -0.0432 0.0321 1.0000 3.750 0.6209 0.01086 0.00340 -0.0422 0.0321 1.0000 4.000 0.6432 0.01106 0.00361 -0.0412 0.0316 1.0000 4.250 0.6655 0.01126 0.00383 -0.0402 0.0303 1.0000 4.500 0.6878 0.01148 0.00407 -0.0393 0.0294 1.0000 4.750 0.7100 0.01172 0.00431 -0.0383 0.0275 1.0000 5.000 0.7318 0.01200 0.00460 -0.0372 0.0250 1.0000 5.250 0.7530 0.01235 0.00498 -0.0361 0.0231 1.0000 5.500 0.7775 0.01239 0.00502 -0.0356 0.0219 1.0000 5.750 0.8012 0.01252 0.00516 -0.0349 0.0188 1.0000 6.000 0.8228 0.01284 0.00536 -0.0338 0.0101 1.0000 6.250 0.8439 0.01323 0.00574 -0.0327 0.0083 1.0000 6.500 0.8650 0.01363 0.00620 -0.0315 0.0075 1.0000 6.750 0.8858 0.01407 0.00674 -0.0303 0.0069 1.0000 7.000 0.9060 0.01457 0.00731 -0.0290 0.0065 1.0000 7.250 0.9258 0.01511 0.00793 -0.0277 0.0061 1.0000 7.500 0.9443 0.01577 0.00868 -0.0262 0.0057 1.0000 7.750 0.9615 0.01658 0.00958 -0.0244 0.0054 1.0000 8.000 0.9758 0.01765 0.01077 -0.0223 0.0052 1.0000 8.250 0.9935 0.01838 0.01161 -0.0207 0.0051 1.0000 8.500 1.0104 0.01918 0.01250 -0.0191 0.0050 1.0000 8.750 1.0261 0.02009 0.01352 -0.0173 0.0049 1.0000 9.000 1.0413 0.02106 0.01460 -0.0154 0.0048 1.0000 9.250 1.0563 0.02203 0.01569 -0.0136 0.0047 1.0000 9.500 1.0726 0.02279 0.01656 -0.0120 0.0043 1.0000 9.750 1.0856 0.02392 0.01782 -0.0100 0.0043 1.0000 10.000 1.0977 0.02489 0.01892 -0.0079 0.0040 1.0000 10.250 1.1069 0.02610 0.02028 -0.0053 0.0039 1.0000 10.500 1.1152 0.02735 0.02167 -0.0028 0.0038 1.0000 10.750 1.1217 0.02880 0.02329 -0.0002 0.0037 1.0000 11.000 1.1271 0.03031 0.02496 0.0023 0.0037 1.0000 11.250 1.1308 0.03198 0.02681 0.0048 0.0036 1.0000 11.500 1.1331 0.03369 0.02868 0.0070 0.0035 1.0000 11.750 1.1336 0.03563 0.03080 0.0091 0.0035 1.0000 12.000 1.1307 0.03800 0.03337 0.0111 0.0034 1.0000 12.250 1.1276 0.04040 0.03594 0.0125 0.0034 1.0000 12.500 1.1205 0.04342 0.03916 0.0138 0.0034 1.0000 12.750 1.1118 0.04673 0.04267 0.0145 0.0034 1.0000 13.000 1.1049 0.04989 0.04594 0.0145 0.0032 1.0000 13.250 1.0942 0.05387 0.05009 0.0140 0.0032 1.0000 13.500 1.0772 0.05907 0.05548 0.0127 0.0032 1.0000 13.750 1.0617 0.06472 0.06138 0.0105 0.0033 1.0000 14.000 1.0477 0.07043 0.06722 0.0076 0.0032 1.0000 14.250 1.0282 0.07814 0.07515 0.0032 0.0033 1.0000 14.500 1.0120 0.08578 0.08288 -0.0016 0.0032 1.0000 14.750 0.9857 0.09719 0.09454 -0.0086 0.0033 1.0000 15.000 0.9606 0.10864 0.10613 -0.0153 0.0033 1.0000